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Is this correct A uniform supersonic flow of a calorically perfect gas with gamma = 1.4, a Mach number of 2.0, and an up-stream static

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A uniform supersonic flow of a calorically perfect gas with gamma = 1.4, a Mach number of 2.0, and an up-stream static pressure of 100 kPa flows over a geometry as shown in figure below. Determine the downstream pressure

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